RU2327605C1 - Miniature airplane - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: miniature airplane has a biplane-type airframe with shortened lower wings the upper wings are provided with end ailerons (2) that are, in fact, turning ends of the wings. Engine nacelles (4) are suspended between the upper and lower wings by means of inclined posts (5,6) and are arranged beyond the wing rear edges.

EFFECT: higher strength and reliability.

2 dwg

Description

The invention relates to the field of aeronautical engineering, in particular to the design of an airplane glider.

Numerous monoplane-type glider designs are known that carry engine nacelles on the wings.

The disadvantage of such aircraft designs is the large wingspan, which complicates their operation, and in case of emergency situations in flight and especially during landing, it can lead to tragic consequences.

Also known is a plane containing a biplane-type glider with shortened lower wings, the upper wings being equipped with end ailerons (I.V. Radchenko, V.P. Kramchaninov, V.P. Dubrinsky, “AN-2 PLANE, M., Transport, 1974, see pages 1-15, 32).

The purpose of the invention is to eliminate the above disadvantages, to develop a more robust and rigid structure of the aircraft glider with a significantly reduced wingspan while maintaining, handling and carrying capacity of the aircraft.

This goal is achieved by developing the design of a biplane-type airframe with end ailerons, which are the wings ending in opposite directions.

The present invention considers a design variant of the airframe with end ailerons located on the upper wings, but similar ailerons can also be installed on the lower wings.

Figure 1 schematically shows a part of the airframe of the proposed design with a left engine nacelle and wings. Front view.

Figure 2 schematically shows the upper and lower wings with an engine nacelle. Side view. Aileron of the upper wing is in working position.

This glider contains the upper wings 1 with ailerons, the lower wings 3 and the nacelles of the engines 4, suspended between the upper and lower wings by means of struts 5 and 6.

As shown in figure 2, the nacelles 4 by means of inclined racks 5 and 6 are displaced to the tail of the aircraft and extended beyond the trailing edges of the wings, which makes it possible to use the entire area of the wings to create lift.

The airframe layout of the proposed design is the most rational for the following reasons:

1. The additional lifting force created by the shortened lower wings 3 makes it possible to reduce the overall wingspan, their cantileverness, and a tendency to vibrations, making the aircraft more compact.

2. The fuselage, wings 1 and 3 and the nacelles 4, suspended between the wings on the uprights 5 and 6, form a closed rigid circuit that reduces possible vibrations and increases the strength of the airframe as a whole.

3. Double wings provide a more reliable and stiffer suspension of the nacelles 4 at a considerable distance from the fuselage, which increases the safety and comfort of the aircraft.

4. End ailerons 2 due to its width over the entire wing will provide sufficient controllability of the aircraft, acting on a reduced shoulder.

The glider of the proposed design will find application in the creation of large-capacity aircraft that do not require high maneuverability.

The use of a biplane-type glider in the designs of low-speed, economical transport aircraft will open up new advantages of this arrangement, and will increase the reliability and comfort of heavy aircraft.

Claims (1)

A compact aircraft containing a biplane-type glider with shortened lower wings, the upper wings being equipped with end ailerons, characterized in that the end ailerons are rotatable wing ends, and the engine nacelles are suspended between the upper and lower wings by means of inclined struts, and the nacelles are extended outside the rear the edges of the wings.

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